Missile

ABSTRACT

The invention concerns a missile, in particular a guided missile, having stabilizing wings and a solid fuel propulsion motor. The fuel of the propulsion motor is divided into two separate fuel charges located axially spaced in the missile. The portion of the interior of the missile between the two fuel charges consists of an empty space, into which the fuel charges deliver their combustion gases and which is surrounded by an annular member forming the external shell of the missile between the two fuel charges and comprising the jet nozzles for the propulsion motor. The two fuel charges have such relative sizes and locations in the missile that their common gravity center coincides substantially with the total gravity center of the missile. The stabilizing wings are attached to the annular member comprising the jet nozzles and are located circumferentially between said jet nozzles.

States Patent Jacobson et al.

[451 Aug. 15, 1972 Primary Examiner-Verlin R. Pendegrass Att0rneyHane, Baxley & Spiecens 5 7] ABSTRACT The invention concerns a missile, in particular a guided missile, having stabilizing wings and a solid fuel propulsion motor. The fuel of the propulsion motor is divided into two separate fuel charges located axially spaced in the missile. The portion of the interior of the missile between the two fuel charges consists of an empty space, into which the fuel charges deliver their combustion gases and which is surrounded by an annular member forming the external shell of the missile between the two fuel charges and comprising the jet nozzles for the propulsion motor. The two fuel charges have such relative sizes and locations in the missile that their common gravity center coincides substantially with the total gravity center of the missile. The stabilizing wings are attached to the annular member comprising the jet nozzles and are located circumferentially between said jet nozzles.

2 Claims. 1 Drawing Figure MISSILE [72] Inventors: Gunnar Jacobson; Olof Bertil Olsson, both of Karlskoga, Sweden [73] Assignee: Aktiebolaget Bofors, Bofors, Sweden [22] Filed: May 28, 1970 [21] App1.No.: 41,373

[30] Foreign Application Priority Data June 6, 1969 Sweden ..8063/69 [52] US. Cl ..244/3.27, 102/493 [51] Int. Cl ..F42b 13/32 [58] Field of Search .....102/49.3; 244/31, 3.22, 3.27

[56] References Cited UNITED STATES PATENTS 2,489,953 11/1949 Burney ..l02/49.3 2,503,271 4/1950 Hickman ..l02/49.3 2,816,721 12/1957 Taylor ..244/3.l X 3,013,494 12/1961 Chanut ..244/3.22 3,127,838. 4/1964 Morath et a1 ..244/3.27

fig T i! iii I i v; x .1

PATENTED 3.684.215

GUN/VAR UMCOBSON OLOF BERT/L OLSSO/V B Ywm 96 A 7' TORNEYS I I.\'VE.\TORS MISSILE The present invention is related to missiles and in particular guided missiles having a solid fuel or powder propulsion motor and stabilizing wings for stabilizing the missile in its flight.

If a missile is to have a stable flight and also be easily guidable, the aerodynamic pressure center of the missile must be located rearwards from but comparatively close to the gravity center of the missile. This means that the stabilizing wings of the missile should be located close to the gravity center of the missile. In order to prevent that the gravity center of the missile is displaced when the fuel of the propulsion motor is consumed, the fuel charge of the propulsion motor should also be located in the missile so as to have its gravity center close to or coinciding with the total resulting gravity center of the missile. These two simultaneous requirements have as a result that the stabilizing wings of the missile and the fuel charge of the propulsion motor should be located at the same part of the missile. This causes difficult space problems. The outer shell or wall of the missile is generally made as thin as possible in order to obtain a low weight and a small total external diameter of the missile. The stabilizing wings attached to the external shell of the missile are subject to very considerable forces, however, wherefore the fastening members for the stabilizing wings and the portion of the missile shell supporting these fastening members must be dimensioned to have a considerable strength. If the stabilizing wings are to be located at the portion of the missile where also the fuel charge of the propulsion motor is located, the fastening means for the wings must consequently project into the internal space in the missile where the fuel charge of the propulsion motor should be located, or alternatively the total external diameter of the missile must be increased so as to give sufficient space for the fastening means for the stabilizing wings. The latter alternative is very disadvantageous, as it impairs very seriously the aerodynamic properties of the missile and also causes an increase of the maximum external diameter of the missile, which in its turn causes that a launching tube for the missile must have a correspondingly large diameter. The radial space necessary for the fastening members for the stabilizing wings is especially large if, as in most cases, it shall be possible to fold the wings to a position close to the external surface of the missile in order to reduce the necessary space for the missile when being stored and transported and to make it possible to tire the missile through a launching tube.

The design problems mentioned above are made still more complicated, if for any reason the jet or thrust nozzles of the propulsion motor cannot be located in the rear end of the missile. In such a case the propulsion motor must be provided with a plurality of jet nozzles which are equally spaced around the missile so as to have their openings in the circumferential surface of the missile and which are pointed obliquely rearwards relative the intended direction of flight of the missile. If these jet nozzles produce equally large thrusts, the total resulting thrust will coincide with the symmetry axis of the missile and be directed through the gravity center of the missile, whereby the propulsion motor will not produce any moments which tend to tip the missile or displace it from its path and which must be compensated for by the guide means of the missile. However, it

is difficult to secure that all jet nozzles always produce equally large thrusts. Therefore the jet nozzles of the propulsion motor should preferably be located comparatively close to the gravity center of the missile, whereby the tilting moment upon the missile becomes comparatively small if the jet nozzles should not produce equally large thrusts. At the same time the nozzles must be located in such a manner that the combustion gases ejected from the nozzles do not produce any aerodynamic disturbances upon the missile or give cause to any other damages upon the missile. Thus, for instance the nozzles shall not have their openings located in front of the stabilizing wings. These requirements mean that also the jet nozzles of the propulsion motor should be located substantially at the same portion of the missile where, as mentioned above, also the stabilizing wings as well as the fuel charge of the propulsion motor should be located. It is obvious that this makes the design of the missile still more complicated with respect to the location of the stabilizing wings, the fuel charge of the propulsion motor and the jet nozzles of the motor.

The principal object of the invention is therefore to provide an improved missile, in particular a guided missile, having such a design that all the above mentioned demands with respect to the location of the stabilizing wings, the fuel charge of the solid fuel propulsion motor and the jet nozzles of the propulsion motor are satisfied.

An unguided missile having a solid fuel propulsion motor is known in the prior art (the French patent specification 839 861 in which the fuel of the propulsion motor is divided into two portions or charges, which are disposed axially spaced in the missile so as to deliver their combustion gases to jet nozzles mounted in an annular member forming the external shell of the missile between the two fuel charges. In this prior art missile the principal object is to obtain such a location of the bursting or service charge of the missile that the gravity center of this service charge coincides with or is located very close to the total gravity center of the missile. For this purpose the service charge is located between the two propellent fuel charges of the propulsion motor so as to fill substantially completely the interior of the missile between the two propellent fuel charges. This causes the very serious disadvantage that the flow path for the combustion gases from the propellent fuel charges to the jet nozzles will be very narrow and that only comparatively small size jet nozzles can be used. As a consequence this prior art arrangement cannot be used for high velocity missiles. Furthermore, the hot propulsion gases will flow very close to the service charge, which may as a consequence assume an unpermissible high temperature. For want of space it is also impossible to mount the stabilizing wings close to the gravity center of the missile, but these must be located at the rear end of the missile.

In the missile according to the present invention the solid propellent fuel of the propulsion motor, just as in the prior art missile described in the foregoing, is divided into two separate fuel charges located axially spaced in the missile so as to deliver their combustion gases to jet nozzles mounted in an annular member forming the external shell of the missile between the two fuel charges. However, the missile according to the invention is characterized in that the two propellent fuel charges have such relative sizes and locations that their common gravity center substantially coincides with the total gravity center of the missile, that the portion of the interior of the missile surrounded by said annular member comprising the jet nozzles constitutes an empty space into which said two fuel charges deliver their combustion gases in common, and that the stabilizing wings are attached to said annular body circumferentially between the jet nozzles.

Thus, in the missile according to the invention, contrary to the prior art missile described in the French patent specification mentioned in the foregoing, the solid propellent fuel of the propulsion motor and not the service charge of the missile is arranged and located so as to have its gravity center coinciding with the total gravity center of the missile. This is a very important feature, as explained in the foregoing, as the propellent fuel is consumed during the flight of the missile and this should not cause any displacement of the total gravity center of the missile. Furthermore, in the missile according to the invention the portion of the interior of the missile between the two propellent fuel charges consists of an empty space, whereby it is very easy to provide very large flow areas for the combustion gases from the fuel charges to the jet nozzles and additionally sufficient space is available also for large jet nozzles. It is also possible to give the annular member comprising the jet nozzle sufficient dimensions and strength and such a shape that the stabilizing wings can be mounted on this member without any increase of the external diameter of the missile being necessary.

In the following the invention will be further described with reference to the accompanying drawing which shows by way of example an embodiment of a missile according to the invention. The drawing shows in axial section only the portion of the missile comprising the propulsion motor of the missile and the stabilizing wings and the jet nozzles of the propulsion motor; the axial sections in the upper half and the lower half of the drawing respectively being taken along different planes in such a manner that the upper half of the drawing shows an axial section through a jet nozzle for the propulsion motor, whereas the lower half of the drawing shows an axial section containing one of the stabilizing wings of the missile.

The missile illustrated by way of example in the drawing has the intended direction of flight indicated by an arrow 1 and is provided with a solid fuel propulsion motor, the solid fuel of which is divided into two separate portions or charges 2 and 3. These two fuel charges are located axially spaced in the missile so as to be separated by an internal space 4 in the missile surrounded by the external shell of the missile. The two fuel charges 2 and 3 are provided to deliver their combustion gases to this space 4 and have in conventional manner conical recesses or bores 2a and 3a respectively facing the space 4.

The portion of the external shell of the missile surrounding the empty space 4 consists of an annular member 5. As obvious from the drawing this annular member 5 may, without any intrusion upon the necessary space for the fuel charges 2 and 3 for the propulsion motor and without any increase of the total external diameter of the missile, be given such dimensions and strength and such a shape that it can support not only the jet nozzles 7 of the propulsion motor (only one being shown in the drawing) but also the stabilizing wings 6 of the missile (only one being shown in the drawing).

The missile according to the invention illustrated by way of example in the drawing is provided with four stabilizing wings 6 equally spaced around the missile and with four jet nozzles 7 for the propulsion motor also equally spaced around the missile. The stabilizing wings 6 and the propulsion nozzles 7 are located alternatingly in the circumferential direction around the missile.

As can be seen from the drawing, the annular member 5 supporting the stabilizing wings 6 and the motor nozzles 7 is preferably formed with recesses 8 in which the motor nozzles 7 and the support member 9 for the stabilizing wings 6 are located so that no parts of the motor nozzles 7 or the support members 9 for the wings project radially outside the external circumferential surface of the missile. This is obviously possible, even if as in the illustrated embodiment the support member 9 for the stabilizing wings 6 are designed to permit the wings to be folded to a position close to the external surface of the missile and therefore require a considerable space, in particular in the radial direction. The central portion 4a of the space 4, to which the fuel charges 2 and 3 deliver their combustion gases, must only be sufficiently large to provide a sufficient flow area for the combustion gases from the fuel charge 3 to the nonles 7.

The recesses 8 in the annular member 5 may consist of a separate recess for each motor nozzle 7 and each wing bracket 9 respectively or alternatively consist of a single annular recess extending continuously and circumferentially around the member 5 and containing all motor nozzles 7 and wing brackets 9. The invention makes it possible, without any increase of the maximal external diameter of the missile being necessary, to locate the stabilizing wings 6 as well as the motor nozzles 7 in the desired position close to the gravity center of the missile and at the same time to locate the gravity center of the solid fuel of the propulsion motor, that is the common gravity center of the two fuel charges 2 and 3, so as to coincide with or be very close to the total gravity center of the missile. Although the stabilizing wings 6 and the motor nozzles 7 are located very close to each other in a very space saving manner, the gas jets from the nozzles will not hit the stabilizing wings and consequently will not damage these or give cause to any aerodynamic disturbances upon the missile.

What is claimed is:

l. A missile comprising:

an elongate, substantially cylindrical external shell;

A solid fuel propulsion motor including two separate fuel charges disposed axially spaced apart within said shell to define a space therein, said fuel charges delivering their combustion gases directly to said space between the fuel charges;

said fuel charges having relative sizes and locations within said shell such that the common center of gravity thereof substantially coincides with the total center of gravity of the missile and relative rates of burning such that their common center of gravity remains substantially stationary relative the with said empty space and their outlet ends are missile during the burning of the charges and said located outside of the shell;

space between the fuel charges being located to aplurality of stabilizing wings; and

coincide substantially with the location of said mounting means on said annular member equally circenter of gravity; 5 cumferentially spaced thereon and intermediate an annular member encircling said space and form- Said eXhauSt no e ing an annular portion of said shell between aid 2. A missile as claimed in claim 1 wherein said annut f l h lar member has recessed wall portions protruding into a plurality of open ended exhaust nozzles for the Said Space, S'aid l 'f l "Q f Said moulltlflg combustion gases generated by Said f charges 10 means for said stabilizing wings being located within mounted equally circumferentially spaced on said said recessesannular member so their inlet ends communicate 

1. A missile comprising: an elongate, substantially cylindrical external shell; A solid fuel propulsion motor including two separate fuel charges disposed axially spaced apart within said shell to define a space therein, said fuel charges delivering their combustion gases directly to said space between the fuel charges; said fuel charges having relative sizes and locations within said shell such that the common center of gravity thereof substantially coincides with the total center of gravity of the missile and relative rates of burning such that their common center of gravity remains substantially stationary relative the missile during the burning of the charges and said space between the fuel charges being located to coincide substantially with the location of said center of gravity; an annular member encircling said space and forming an annular portion of said shell between said two fuel charges; a plurality of open ended exhaust nozzles for the combustion gases generated by said fuel charges mounted equally circumferentially spaced on said annular member so their inlet ends communicate with said empty space and their outlet ends are located outside of the shell; a plurality of stabilizing wings; and mounting means on said annular member equally circumferentially spaced thereon and intermediate said exhaust nozzles.
 2. A missile as claimed in claim 1 whErein said annular member has recessed wall portions protruding into said space, said exhaust nozzles and said mounting means for said stabilizing wings being located within said recesses. 